CN103608546B - The impinging cooling of turbine blade or wheel blade - Google Patents
The impinging cooling of turbine blade or wheel blade Download PDFInfo
- Publication number
- CN103608546B CN103608546B CN201280030567.2A CN201280030567A CN103608546B CN 103608546 B CN103608546 B CN 103608546B CN 201280030567 A CN201280030567 A CN 201280030567A CN 103608546 B CN103608546 B CN 103608546B
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- CN
- China
- Prior art keywords
- hollow aerofoil
- impact tube
- wall section
- aerofoil
- turbine assembly
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
- F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/50—Building or constructing in particular ways
- F05D2230/51—Building or constructing in particular ways in a modular way, e.g. using several identical or complementary parts or features
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/50—Building or constructing in particular ways
- F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/61—Assembly methods using limited numbers of standard modules which can be adapted by machining
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
- Y10T29/49337—Composite blade
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to turbine assembly (10), including: substantially hollow aerofoil (12), at least one wall section (14,14 '), described wall section is arranged in the side (16 of spanwise (18) orientation being basically perpendicular to hollow aerofoil (12) of hollow aerofoil (12), 16 '), and there is the offer that is positioned at least one wall section (14,14 ') the described at least insertion hole (20) close to the entrance of hollow aerofoil (12), at least impact tube (22,22a), described at least impact tube is via wall section (14,14 ') the insertion hole (20) in is inserted in hollow aerofoil (12), to be placed in hollow aerofoil (12), and extend along at least spanwise (18) of hollow aerofoil (12). according to the present invention, at impact tube (22, 22a) under the assembled state in hollow aerofoil (12), impact tube (22, at least jut (24 22a), 24a) along a direction substantially perpendicular the direction (26) of spanwise (18) orientation at wall section (14, 14 ') extend in edge (28) scope in insertion hole (20), wherein, described jut (24, 24a) with wall section (14, 14 ') at least some of (30) are overlapping, impact tube (22, the contiguous described jut (24 of lap (76) 22a), 24a) arrange, described lap contacting wall section (14, 14 ') edge (28) in insertion hole (20), described jut (24, 24a) it is formed integrally with each other by parts with described lap (76).
Description
Technical field
The present invention relates to the turbine assembly of airfoil shape, such as turbine rotor blade and stator vane. The invention still further relates to a kind of method for being assembled into by impact tube in this assembly.
Background technology
Modern wind turbine generally runs at very high temperatures. Turbine blade and/or affecting effectively running of turbine of stator vane are harmful by temperature, and can cause the deformation of blade or wheel blade and possible fault in extreme circumstances. In order to overcome this risk, high temperature turbines can include the hollow blade or the wheel blade that combine so-called impact tube for cooling purposes.
These so-called impact tubes are the hollow pipes radially extended in blade or wheel blade. Air is forced into these pipes, advances along these pipes, and pours in the space between described pipe and hollow blade or the inner surface of wheel blade via suitable hole. This generates internal air stream, be used for cooling down blade or wheel blade.
Generally, blade and wheel blade have hollow structure by casting. Impact tube can insert hollow structure from one end or the other end, and generally welds together with hollow structure, with fix in position. When the size of the size in impinging cooling region and the airfoil area thus with most high cooling efficiency is limited to the size of opening (impact tube inserts in aerofoil or blade or wheel blade via this opening) respectively, it may occur that problem.
Impact tube is implemented with different boxes or shelly body from EP1380725A2 is known. These bodies are respectively provided with about but are not more than the size of opening, to be inserted by described body in the room of blade or wheel blade, and are then inserted through described opening.
US4798515A discloses a kind of turbine assembly, and including substantially hollow aerofoil and wall section (fixing trunnion support part), wall section is arranged in the side of the spanwise orientation being substantially perpendicular to hollow aerofoil of hollow aerofoil.Insert in the recessed described wall section in hole, it is provided that close to the entrance of hollow aerofoil.
The impact tube of turbine assembly is positioned in hollow aerofoil via gudgeon. The flared elastic part support of impact tube coordinates or is press-fitted in the ingate of gudgeon. Gudgeon mates wall section (namely fixing trunnion support part) by gudgeon mounting portion and is placed in hollow aerofoil.
The first object of the present invention is to provide a kind of for impact tube is assembled into the method in the hollow aerofoil of airfoil shape turbine assembly (such as turbine rotor blade and stator vane), it can reduce disadvantages mentioned above, especially promotes the more effective aerofoil of aerodynamic and gas turbine engine component.
The second object of the present invention is to provide a kind of favourable airfoil shape turbine assembly, such as turbine rotor blade and stator vane. The third object of the present invention there is provided a kind of favourable impact pipe for cooling purposes being used in this assembly.
Summary of the invention
Correspondingly, the invention provides a kind of turbine assembly, including: substantially hollow aerofoil; At least wall section, described at least wall section is arranged in the side of the spanwise orientation being basically perpendicular to hollow wall of hollow aerofoil, and has at least insertion hole providing the entrance close to hollow aerofoil being arranged at least one wall section described; At least described in impact tube, at least impact tube inserts in hollow aerofoil via inserting hole, to be placed in hollow aerofoil, and extends at least spanwise of hollow aerofoil.
Namely, under impact tube assembled state in aerofoil, the at least jut of impact tube extends on the direction being basically perpendicular to spanwise orientation in the edge extent inserting hole of wall section, wherein, described jut is at least some of overlapping with wall section, the contiguous described jut of the lap of impact tube is arranged, and abuts the edge inserting hole, and described jut and described lap are formed integrally with each other by parts. Due to creative item, the size in the impinging cooling region of aerofoil can advantageously and significantly increase. Therefore, it can expand the airfoil area with most high cooling efficiency. And, the size cooled region without limitation on assembly inserting hole of wall section. Therefore, can there is bigger degree of freedom when constructing each parts (housing of such as aerofoil, inner or outer platform and/or the insertion hole itself) of turbine assembly. When using this turbine assembly, it is possible to use the conventional sense of existing aerofoil, without intricately and expensively re-constructing these aerofoils. Only needing such as to reduce the size of pin wing/support (pinfin/pedestal) cooled region, this can complete simply by the core somewhat revising aerofoil foundry goods. Therefore, it can advantageously provide each effective turbine assembly or turbine. Additionally, due to the Integral design of the embodiment of jut and lap, impact tube can be arranged in aerofoil by loss-prevention ground (loss-proof).
Turbine assembly is used for referring to provides the assembly for turbine (such as combustion gas turbine), and wherein, this assembly has at least aerofoil. Preferably, turbine assembly includes turbine cascade and/or the wheel with aerofoil circumferentially, and/or is arranged in the outer and inner platform of aerofoil opposite end. In this article, " substantially hollow aerofoil " refers to the aerofoil with housing, and wherein, housing surrounds at least one cavity. The such as structure of rib, track or dividing plate will not hinder the definition of " substantially hollow aerofoil ", and the different cavitys in aerofoil are separated from each other by described structure, and such as extends in the spanwise of aerofoil.Preferably, aerofoil is hollow. Especially, in being described below, it is called that the substantially hollow aerofoil of aerofoil has two cooled regions, is namely positioned at the impinging cooling region of aerofoil leading edge and is positioned at the existing pin wing/stent cools region of trailing edge. These regions can be spaced apart via rib. Wall section is for referring to the region of the cavity at least some of, especially aerofoil defining cavity of turbine assembly. Wall section can be the region of the housing of aerofoil, or preferably, is the region of inner platform and/or outer platform. Embodiment according to inner platform and outer platform, can use and have multiple different platform and be arranged in the same kind of airfoil surface configuration inserting hole of platform.
The layout scope " being basically perpendicular to " side of spanwise also should occupy this side of wall section relative to spanwise deviation about 30 ��. Preferably, described side is arranged perpendicularly to spanwise. The spanwise of hollow aerofoil is defined as substantially perpendicular to, is preferably perpendicular to the direction that the direction from the leading edge of aerofoil to trailing edge extends. " insertion hole " is used for referring to opening, otch and/or hole, especially through hole, inserts hole and is used for, is ready for, designs for and/or implements inserting in each aerofoil or its cavity near few impact tube. It is therefoie, for example, insertion hole and impact tube match each other in size, material properties etc., to allow to insert impact tube.
Impact tube assembled state in aerofoil represents state when turbine assembly is used for work, especially represents turbine assembly or the respective duty of turbine. Jut refers to the part prominent from the major part of impact tube of impact tube. Major part preferably limits the substantial scope especially in the spanwise direction of impact tube. Additionally, the edge inserting hole is used for referring to end, border, mechanical stopping piece and/or the restriction to insertion hole. And, term " vicinity " should be understood to adjoin, border on and/or adjacent. Lap is for referring to the structure extended within the scope of the span of jut along spanwise. Preferably, lap abuts described edge vertically and/or extends within the scope of the whole span inserting hole along spanwise. In general, it is also feasible that lap only extends in a part of scope of the span in insertion hole. In this article, word " forming " is used for referring to jut and lap and is molded by parts.
Advantageously, hollow aerofoil includes single cavity. But the present invention also can realize including the hollow aerofoil of two or more cavitys, each cavity holds according to the impact tube of the present invention and/or is the part in pin wing/stent cools region.
As it has been described above, hollow aerofoil includes trailing edge and leading edge. In a preferred embodiment, the jut of impact tube is upwardly extending towards the side of trailing edge orientation. This free space causing being efficiently used cavity, and directly cool down this region. Additionally, jut can have through hole. Therefore, the pin wing/stent cools region of guiding non-percussion is can be easy to via the cooling medium that impact tube is directed.
Preferably, impact tube substantially extends completely through the span of hollow aerofoil, causes effectively cooling down aerofoil. And, it is advantageous to, impact tube has the stepped profile abutting the edge inserting hole. Stepped profile is for referring to the structure with at least one step of impact tube. Stepped profile is preferably made up of the wall section of jut and the wall section of lap. According to creative embodiment, it is easy to provide impact tube and being directed at of inserting hole. Additionally, stepped profile ensures location, loss-prevention ground impact tube. The forward part towards leading edge orientation of impact tube also can have a roughly the same profile of the inner surface of the leading edge with hollow aerofoil and/or jut also can have the profile that the inner surface of trailing edge with hollow aerofoil is roughly the same.
In a further beneficial embodiment, impact tube is formed by least two separate section. According to creative solution, using the impact tube of two or more parts, especially assembled portion branch aerofoil can being allowed to have bigger cavity independently, even if there being little insertion hole also such. This is by being avoided Rig up error to add the aerodynamic efficiency of aerofoil, and thereby increases the efficiency of turbine. And, at least two separate section is formed by rear portion and front portion, and wherein, especially, rear portion disposes towards the trailing edge of hollow aerofoil, and the anterior leading edge towards hollow aerofoil disposes. Additionally, jut is arranged in rear portion, and towards trailing edge orientation. By the layout that this is favourable, the free space of cavity is efficiently used for directly cooling down this region by jut.
It is also contemplated that impact tube is formed by three separate sections, especially it is the front portion of impact tube, middle part and rear portion, wherein, front portion can dispose towards the leading edge of hollow aerofoil, and middle part can be located at the centre of each hollow aerofoil or its cavity, and/or rear portion can dispose towards the trailing edge of hollow aerofoil. Order when assembling described part can be first rear portion, is followed by middle part, and the 3rd is anterior. Assembling middle part and anterior order also can be inverted in the middle part of behind first front portion.
Advantageously, at least two separate section all substantially extends completely through the span of hollow aerofoil, causes effectively cooling down aerofoil. It is also contemplated that at least one at least two separate section extends only through a part for the span of hollow aerofoil.
In an advantageous embodiment, anterior by rear portion lock into place in hollow aerofoil, thus prevent rear portion therefrom hollow wing emaciated face from. Therefore, it can the alignment completing rear portion when not having high constructive effort in aerofoil. This locking process can via those skilled in the art can any mechanism regulate, for instance via the locking component being arranged between front and rear, bonding force and/or preferably via press-fit and/or form fit. Therefore, there is no need to any extra parts rear portion fastening put in place. Therefore, it can the cost saved for part and assembly. In the embodiment with more than two separate section, front portion can be used for all other parts lock into places.
Preferably, locking process is completed via the form fit between stepped profile and the edge inserting hole of impact tube, thus being directed at rear portion in aerofoil rightly.
In order to provide the turbine assembly of the satisfied alignment having good cooling attribute and impact tube in aerofoil, hollow aerofoil includes at least distance piece being positioned at the inner surface of hollow aerofoil, predetermined distance with the described surface of hollow aerofoil to be kept into by impact tube. For the simple construction of impact tube and straight take one's seat, distance piece is preferably implemented as projection or stop pin or rib.
In a further beneficial embodiment, hollow aerofoil is turbine blade or wheel blade, for instance nozzle guide vanes.
Present invention also offers the impact tube with matrix, be positioned at the substantially hollow aerofoil with at least wall section of turbine assembly body portion. Impact tube or matrix include at least jut respectively, and wherein, jut forms ladder platform. Stepped profile is preferably implemented into the edge inserting hole of contacting wall section, to establish form fit under the assembled state in hollow aerofoil between stepped profile and the edge inserting hole. Therefore, may readily provide impact tube and being directed at of inserting hole.In this article, " matrix " is for referring to the structure of shape and/or the form substantially with impact tube.
Impact tube according to the present invention can be used in existing aerofoil, to increase their cooling effectiveness. Therefore, when using creative impact tube, it is not necessary to re-construct the conventional housing of this aerofoil, to adopt conventional housing in restriction in the structure of aerofoil cavity. Therefore, it is particularly possible to reduce cost and constructive effort, because impact tube is low cost object.
Present invention also offers a kind of method for being assembled into by impact tube in the substantially hollow aerofoil of turbine assembly. Said method comprising the steps of:
-impact tube is inserted in hollow aerofoil via the insertion hole of wall section, wherein, described wall section is arranged in the side of the spanwise orientation being basically perpendicular to hollow aerofoil of hollow aerofoil,
-at least jut of impact tube is adjusted in place, the direction making jut spanwise orientation along a direction substantially perpendicular extends in the edge extent inserting hole of wall section, wherein, jut is at least some of overlapping with wall section, the lap adjacent protrusions part of impact tube is arranged, and the edge inserting hole of contacting wall section, jut and lap are formed integrally with each other by parts.
Due to this creativeness method, insert the size cooled region without limitation on assembly in hole. Therefore, the size in the impinging cooling region of aerofoil can advantageously and significantly increase. Therefore, the airfoil area with most high cooling efficiency can be expanded. Therefore, can there is bigger degree of freedom when constructing each parts of turbine assembly. As a result, it is possible to advantageously assemble and thus provide each effective turbine assembly or turbine. Additionally, due to the Integral design of jut and lap, impact tube can be arranged or be maintained in aerofoil in loss-prevention ground.
Term " is adjusted in place " for referring to via being passively or actively the process that mechanism regulates. Driven member can have the feature of such as impact tube itself or impact tube material, such as flexible or elastic. It addition, driving mechanism can such as use the driving part extending and thus positioning for jut of jut, such as spring, and/or use the external force for positioning.
Advantageously, impact tube includes at least rear portion and front portion, after being adjusted in place at rear portion, inserts in hollow aerofoil by front portion via the contiguous rear portion, insertion hole of wall section, and is adjusted in place in hollow aerofoil. The present invention is based on the recognition that, by using two or more part impact tubes can avoid the restriction inserting space inserting hole; Wherein, each part can individually packaged enter in hollow aerofoil. Each part is slided independently in hollow aerofoil, namely slides independently in the cavity of hollow aerofoil, then moves into their appropriate place or position.
Preferably, via front portion by the position at rear portion lock into place in hollow aerofoil, thus prevent rear portion therefrom hollow wing emaciated face from. Especially, via press-fit and/or form fit by the position at rear portion lock into place in hollow aerofoil, cause being directed at rightly rear portion in aerofoil. If preferably promoting this locking via the form fit between the stepped profile of impact tube and the edge inserting hole, then can obtain favourable loss-prevention and arrange.
According to creative method, especially, it is provided that turbine assembly, wherein, impact tube is formed by two separate sections.In addition, two separate sections are positioned in substantially hollow aerofoil via the insertion hole in wall section, described wall section is arranged in the side of the spanwise orientation being basically perpendicular to hollow aerofoil of hollow aerofoil, wherein, at assembled state, the direction of the jut at one of impact tube or two separate sections or rear portion spanwise orientation along a direction substantially perpendicular extends in the edge extent inserting hole of wall section, wherein, jut is at least some of overlapping with wall section, the lap adjacent protrusions part of impact tube is arranged, and abut the edge inserting hole, jut and lap are formed integrally with each other by parts.
Accompanying drawing explanation
Below with reference to the accompanying drawings the present invention is described, in accompanying drawing:
Fig. 1 illustrates the perspective view of the turbine assembly with the impact tube inserted in aerofoil;
Fig. 2 illustrates from Fig. 1 top view with outer platform and the aerofoil inserting hole looked down;
Fig. 3 illustrates the cross section that the line III-III along Fig. 2 intercepts, it is shown that the impact tube of the insertion of the Fig. 1 formed by two parts;
Fig. 4 a illustrates for the two of the impact tube of Fig. 1 and 3 methods that part is assembled in the cavity of hollow aerofoil are in the first figure inserted during rear section;
What Fig. 4 b illustrated Fig. 4 a method is in the second figure inserted during forward part; And
Fig. 5 illustrates through the cross section with the aerofoil substituting the impact tube implemented.
Detailed description of the invention
In this description, for the sake of simplicity, wheel blade is only mentioned, however, it is understood that present invention can apply to the blade of turbine and wheel blade.
Fig. 1 illustrates the perspective view of turbine assembly 10. Turbine assembly 10 includes substantially hollow aerofoil 12, and hollow aerofoil is embodied as wheel blade, has two cooled regions, is exactly impinging cooling region 58 and pin wing/stent cools region 60. Impinging cooling region is positioned at leading edge 34, and pin wing/stent cools region is positioned at the trailing edge 32 of aerofoil 12. Two wall sections 14,14 ' are arranged in the both sides 16,16 ' of hollow aerofoil 12, and wherein, both sides 16,16 ' are substantially perpendicular to spanwise 18 orientation of hollow aerofoil 12, and are positioned at the opposite end 62,62 ' of aerofoil 12. Wall section 14,14 ' is the region 46 of inner platform 48 and outer platform 50. Each wall section 14,14 ' has insertion hole 20, inserts the impinging cooling region 58 that is arranged to aerofoil 12, hole and is directed at, and provides entrance close to the hollow aerofoil 12 insertion hole of wall section 14 (Fig. 1 only illustrate). Can being provided with some aerofoils 12 in the circumferential direction of unshowned turbine cascade, wherein, all aerofoils 12 are joined to one another via inner platform 48 and outer platform 50.
The housing 64 of hollow aerofoil 12 forms the cavity 66 being arranged in impinging cooling region 58. Impact tube 22 inserts in cavity 66 via inserting hole 20, for the purpose of cooling. Therefore, impact tube 22 is placed in hollow aerofoil 12 with the impact tube 22 assembled state in hollow aerofoil 12. Impact tube 22 extends completely through the span 38 of hollow aerofoil 12 along spanwise 18, and is embodied as matrix 56. Additionally, at turbine assembly 10 run duration, impact tube 22 provides stream 68 for cooling medium (such as air). On the inner surface 54 of hollow aerofoil 12, hollow aerofoil includes many distance pieces 52, to keep impact tube 22 and this surface 54 predetermined distance. Distance piece 52 is embodied as projection or rib, projection or rib and is perpendicular to spanwise 18 and extends.
As in figure 2 it is shown, it illustrates the top view of outer platform 48, the aerofoil 12 of lower section is shown in broken lines, inserts hole 20 and is directed at the cavity 66 of aerofoil 12.But, cavity 66 is more than inserting hole 20 on direction 26, and direction 26 is vertical orientated relative to spanwise 18. In order to insert the impact tube 22 in the region 70 (not being directed at) also taking up cavity 66 with insertion hole 20, impact tube 22 is formed by two separate sections 42,44, as can be seen that from the diagram in detail of Fig. 3. Rear portion 42 that two parts 42,44 are disposed by the trailing edge 32 towards hollow aerofoil 12 and being formed towards the front portion 44 that leading edge 34 disposes. Two parts 42,44 extend completely through the span 38 of hollow aerofoil 12, and concordant with the outer surface 72 of inner platform 48 and outer platform 50.
At impact tube 22 or two respective assembled states of part 42,44, the jut 24 at impact tube 22 or rear portion 42 extends in edge 28 scope inserting hole 20 along direction 26 respectively, and jut 24 is overlapping with the part 30 of wall section 14,14 '. Therefore, jut 24 extends along the direction 36 towards trailing edge 32 orientation. This especially by from Fig. 2 insert hole 20 extend to Fig. 3 insert hole 20 shown in phantom. If drawn, then right line can extend through jut 24. The lap 76 adjacent protrusions part 24 of impact tube 22 is arranged. This lap 76 abuts the edge 28 inserting hole 20, and extends within the scope of the whole span inserting hole 20 along spanwise 18. Jut 24 and lap 76 are moulded integrally with each other by parts and are formed. Impact tube 22 has and jut 24 is formed with ladder platform 40, and ladder platform abuts the edge 28 inserting hole 20. At assembled state, anterior 44 by rear portion 42 lock into place in hollow aerofoil 12, thus preventing rear portion 42 from departing from from aerofoil 12. This locking mechanism regulates via the press-fit between ladder platform 40 and the edge 28 inserting hole 20 of impact tube 22 and form fit.
Referring to Fig. 4 a and 4b, illustrate impact tube 22 is assembled in the method in the hollow aerofoil 12 of turbine assembly 10. At the first number of assembling steps, (I) in hollow aerofoil 12 is inserted via the insertion hole 20 of wall section 14 in the rear portion 42 of impact tube 22. In the second number of assembling steps subsequently, the jut 24 at impact tube 22 or rear portion 42 is adjusted in place, the direction 26 making jut 24 spanwise 18 orientation along a direction substantially perpendicular extends in edge 28 scope inserting hole 20 of wall section 14,14 ', wherein, jut 24 and wall section 14,14 ' at least part of 30 overlapping, the lap 76 adjacent protrusions part 24 of impact tube 22 is arranged, and abutting the edge 28 inserting hole 20, jut 24 and lap 76 are formed integrally with each other (II) by parts. Can such as manually apply force to perform described adjustment. The movement at rear portion 42 by ladder platform 40 with insert hole 20 edge 28 contact restriction (Fig. 4 a).
At the 3rd number of assembling steps, insert anterior 44 in hollow aerofoil 12 at vicinity rear portion 42, the side of trailing edge 34 orientation towards aerofoil 12 via the hole 20 of inserting of wall section 14. Afterwards, rear portion 44 is adjusted in place (III) (Fig. 4 b) in hollow aerofoil 12. In final sum the 4th number of assembling steps, via anterior 44 by the position at rear portion 42 lock into place in hollow aerofoil 12, thus preventing rear portion 42 from departing from (IV) from hollow aerofoil 12, wherein, locking mechanism regulates via the press-fit between ladder platform 40 and the edge 28 inserting hole 20 of impact tube 22 and form fit. Assembled state as can be seen from Figure 3.
Or, the wall facing each other of rear portion 42 and front portion 44 is embodied as has intercommunicating pore (not shown).Additionally, these walls also can be omitted altogether so that they interlock at assembling position, to form single internal cavities (see Fig. 5).
In fig. 5, it is shown that the alternate embodiment of impact tube 22. Still keep identical parts, feature and functional principle are denoted by the same reference numerals substantially. But, in order to distinguish embodiment, letter " a " adds the different reference numbers of the embodiment of Fig. 5 to. Lower example describes the difference being essentially limited to the embodiment with Fig. 1 to 4, wherein, about still keeping the parts of same reference numerals, feature and function, is referred to the description of the embodiment of Fig. 1 to 4.
Fig. 5 illustrates through the cross section with the aerofoil 12 (being similarly formed to 4 with Fig. 1) substituting the impact tube 22a implemented. The embodiment of Fig. 5 is different in that with the embodiment according to Fig. 1 to 4, and impact tube 22a is embodied as single-piece 74. In order to allow the insertion hole 20 via wall section 14 to be inserted in hollow aerofoil 12 by single-piece impact tube 22a, impact tube 22a has the jut 24a formed by flexible material. Or, whole impact tube can be formed by flexible material. Therefore, after impact tube 22a is inserted through insertion hole 20, jut 24a is adjusted in place (not shown in detail) via himself intensity (resilient property because of flexible material). Therefore, at assembled state, jut 24a extends in edge 28 scope inserting hole 20 along the direction 26 being perpendicular to spanwise 18 orientation, and wherein, jut 24a is overlapping with a part 30 for wall section 14,14 '. Additionally, adjacent protrusions part 24a, lap 76 abuts the edge 28 inserting hole 20. Jut 24a and lap 76 are formed integrally with each other by parts.
In general, also can implement insert the edge in hole or there is the whole region of the wall section inserting hole by flexible or elastomeric material.
Another way is that impact tube is embodied as expandable single-piece, and wherein, described single-piece expand into shape as shown in Figure 5 in original place. This can use such as fluid, compression air or more preferably liquid maintain. Such as, liquid filable enters in the double walled housing of impact tube, for expansion. Solidify it addition, liquid may utilize any appropriate methodology (such as polymerization or radiation (UV, IR etc.)), so that shell stability. And, can also be used with shape-memory material and manufacture housing, wherein, instrument (machinery, fluid, gas, liquid) for expand be can be removed after inflation. Or, the single-piece of expansion can utilize those skilled in the art can any method (such as glued or welding) be held in place.
Claims (17)
1. a turbine assembly (10), including: substantially hollow aerofoil (12), at least one wall section (14,14 '), described wall section is arranged in the side (16 of spanwise (18) orientation being basically perpendicular to hollow aerofoil (12) of hollow aerofoil (12), 16 '), and there is the offer that is positioned at least one wall section (14,14 ') the described at least insertion hole (20) close to the entrance of hollow aerofoil (12), at least impact tube (22, 22a), described at least impact tube inserts in hollow aerofoil (12) via inserting hole (20), to be placed in hollow aerofoil (12), and extend along at least spanwise (18) of hollow aerofoil (12), wherein, at impact tube (22, 22a) under the assembled state in hollow aerofoil (12), impact tube (22, at least jut (24 22a), 24a) along a direction substantially perpendicular the direction (26) of spanwise (18) orientation at wall section (14, 14 ') extend in edge (28) scope in insertion hole (20), wherein, described jut (24, 24a) with wall section (14, 14 ') at least some of (30) are overlapping, impact tube (22, the contiguous described jut (24 of lap (76) 22a), 24a) arrange, described lap contacting wall section (14, 14 ') edge (28) in insertion hole (20), described jut (24, 24a) it is formed integrally with each other by parts with described lap (76).
2. turbine assembly as claimed in claim 1, wherein, described hollow aerofoil (12) includes trailing edge (32) and leading edge (34), wherein, impact tube (22, jut (24,24a) 22a) is in the upper extension in direction (36) towards trailing edge (32) orientation.
3. turbine assembly as claimed in claim 1, wherein, described impact tube (22,22a) substantially completely extends through the span (38) of hollow aerofoil (12).
4. the turbine assembly as described in top as arbitrary in above claim, wherein, described impact tube (22,22a) has stepped profile (40), the edge (28) in the insertion hole (20) of described stepped profile contacting wall section (14,14 ').
5. the turbine assembly as described in top as arbitrary in claim 1-3, wherein, described impact tube (22) is by least two separate section (42,44) formed, namely formed by rear portion (42) and anterior (44), described rear portion (42) disposes towards the trailing edge (32) of hollow aerofoil (12), and described front portion (44) dispose towards the leading edge (34) of hollow aerofoil (12).
6. the turbine assembly as described in top as arbitrary in claim 1-3, wherein, described impact tube (22) is formed by least two separate section (42,44), and each separate section substantially completely extends through the span (38) of hollow aerofoil (12).
7. turbine assembly as claimed in claim 5, wherein, described front portion (44) is by described rear portion (42) lock into place in hollow aerofoil (12), thus preventing rear portion (42) from departing from from hollow aerofoil (12).
8. turbine assembly as claimed in claim 5, wherein, described front portion (44) via press-fit and/or form fit by rear portion (42) lock into place in hollow aerofoil (12).
9. turbine assembly as claimed in claim 8, wherein, described front portion (44) via the form fit between the edge (28) in the insertion hole (20) of stepped profile (40) and the wall section (14,14 ') of impact tube (22) by rear portion (42) lock into place in hollow aerofoil (12).
10. the turbine assembly as described in top as arbitrary in claim 1-3 and 7-9, wherein, have and be positioned at wall section (14,14 ') the described wall section (14,14 ') at least insertion hole (20) in is the region (46) of outer platform (48) and/or inner platform (50).
11. the turbine assembly as described in top as arbitrary in claim 1-3 and 7-9, wherein, described hollow aerofoil (12) includes at least distance piece (52) being positioned at the inner surface (54) of hollow aerofoil (12), with by impact tube (22,22a) keeping into predetermined distance with the described surface (54) of hollow aerofoil (12), described distance piece is embodied as projection.
12. turbine assembly as claimed in claim 11, wherein, described distance piece is embodied as stop pin or rib.
13. the turbine assembly as described in top as arbitrary in claim 1-3 and 7-9, wherein, described hollow aerofoil (12) is turbine blade or wheel blade.
14. impact tube (22,22a) is assembled into the method in the substantially hollow aerofoil (12) of turbine assembly (10), said method comprising the steps of:
-by impact tube (22,22a) via wall section (14,14 ') insertion hole (20) is inserted in hollow aerofoil (12), wherein, described wall section (14,14 ') side (16,16 ') (I) of spanwise (18) orientation being basically perpendicular to hollow aerofoil (12) of hollow aerofoil (12) it is arranged in
-by impact tube (22, at least jut (24 22a), 24a) it is adjusted in place, make jut (24, 24a) along a direction substantially perpendicular the direction (26) of spanwise (18) orientation at wall section (14, 14 ') extend in edge (28) scope in insertion hole (20), wherein, jut (24, 24a) with wall section (14, 14 ') at least some of (30) are overlapping, impact tube (22, lap (76) adjacent protrusions part (24 22a), 24a) arrange, and contacting wall section (14, 14 ') edge (28) in insertion hole (20), jut (24, 24a) it is formed integrally with each other (II) with lap (76) by parts.
15. as claimed in claim 14 impact tube (22) is assembled into the method in the substantially hollow aerofoil (12) of turbine assembly (10), wherein, impact tube (22) includes at least rear portion (42) and anterior (44), after rear portion (42) are adjusted in place (II), by front portion (44) via wall section (14,14 ') insertion hole (20) is close to rear portion (42) and inserts in hollow aerofoil (12), and is adjusted in place (III) in hollow aerofoil (12).
16. as claimed in claim 15 impact tube (22) is assembled into the method in the substantially hollow aerofoil (12) of turbine assembly (10), wherein, via anterior (44) by the position of rear portion (42) lock into place in hollow aerofoil (12), thus preventing rear portion (42) from departing from from hollow aerofoil (12).
17. as claimed in claim 16 impact tube (22) is assembled into the method in the substantially hollow aerofoil (12) of turbine assembly (10), wherein, via press-fit and/or form fit by the position of rear portion (42) lock into place (IV) in hollow aerofoil (12).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP11171552.0 | 2011-06-27 | ||
| EP11171552A EP2540969A1 (en) | 2011-06-27 | 2011-06-27 | Impingement cooling of turbine blades or vanes |
| PCT/EP2012/060985 WO2013000691A1 (en) | 2011-06-27 | 2012-06-11 | Impingement cooling of turbine blades or vanes |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103608546A CN103608546A (en) | 2014-02-26 |
| CN103608546B true CN103608546B (en) | 2016-06-08 |
Family
ID=44936631
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201280030567.2A Expired - Fee Related CN103608546B (en) | 2011-06-27 | 2012-06-11 | The impinging cooling of turbine blade or wheel blade |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US9650899B2 (en) |
| EP (2) | EP2540969A1 (en) |
| CN (1) | CN103608546B (en) |
| RU (1) | RU2606004C2 (en) |
| WO (1) | WO2013000691A1 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2016538470A (en) * | 2013-11-25 | 2016-12-08 | ゼネラル エレクトリック テクノロジー ゲゼルシャフト ミット ベシュレンクテル ハフツングＧｅｎｅｒａｌ Ｅｌｅｃｔｒｉｃ Ｔｅｃｈｎｏｌｏｇｙ ＧｍｂＨ | Blade assembly for turbomachines based on modular structure |
| US10655477B2 (en) * | 2016-07-26 | 2020-05-19 | General Electric Company | Turbine components and method for forming turbine components |
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| RU2043508C1 (en) * | 1992-06-15 | 1995-09-10 | Акционерное общество открытого типа "Авиадвигатель" | Cooled working blade of turbine |
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| ITTO20020607A1 (en) | 2002-07-12 | 2004-01-12 | Fiatavio Spa | METHOD FOR THE REALIZATION AND ASSEMBLY OF A COOLING DEVICE IN A BUCKET OF AN AXIAL GAS TURBINE AND BUCKET FOR A |
| US6951444B2 (en) * | 2002-10-22 | 2005-10-04 | Siemens Aktiengesselschaft | Turbine and a turbine vane for a turbine |
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| US8353668B2 (en) * | 2009-02-18 | 2013-01-15 | United Technologies Corporation | Airfoil insert having a tab extending away from the body defining a portion of outlet periphery |
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2011
- 2011-06-27 EP EP11171552A patent/EP2540969A1/en not_active Withdrawn
-
2012
- 2012-06-11 WO PCT/EP2012/060985 patent/WO2013000691A1/en active Application Filing
- 2012-06-11 EP EP12728443.8A patent/EP2723989B1/en not_active Not-in-force
- 2012-06-11 RU RU2013158323A patent/RU2606004C2/en not_active IP Right Cessation
- 2012-06-11 US US14/126,440 patent/US9650899B2/en not_active Expired - Fee Related
- 2012-06-11 CN CN201280030567.2A patent/CN103608546B/en not_active Expired - Fee Related
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| US3540810A (en) * | 1966-03-17 | 1970-11-17 | Gen Electric | Slanted partition for hollow airfoil vane insert |
| US3628880A (en) * | 1969-12-01 | 1971-12-21 | Gen Electric | Vane assembly and temperature control arrangement |
| US4482295A (en) * | 1982-04-08 | 1984-11-13 | Westinghouse Electric Corp. | Turbine airfoil vane structure |
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| CN201474728U (en) * | 2009-08-31 | 2010-05-19 | 中国航空动力机械研究所 | Turbo cooling blade |
Also Published As
| Publication number | Publication date |
|---|---|
| US20140119888A1 (en) | 2014-05-01 |
| RU2606004C2 (en) | 2017-01-10 |
| CN103608546A (en) | 2014-02-26 |
| EP2723989A1 (en) | 2014-04-30 |
| EP2540969A1 (en) | 2013-01-02 |
| WO2013000691A1 (en) | 2013-01-03 |
| RU2013158323A (en) | 2015-08-10 |
| US9650899B2 (en) | 2017-05-16 |
| EP2723989B1 (en) | 2017-01-18 |
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